In this study, the transient aerodynamic performance of an asymmetric airfoil under oscillating turbulence at different angles of attack was studied. Experimental data were used to validate the precision of the numerical simulation approach. The results were obtained by establishing single-and double-wing models of the NACA6412 airfoil with and without disturbance sources. The velocity, pressure, and lift-drag characteristics of the airfoil were investigated. Compared with the single-wing model, the unsteadiness of the double-wing model was more significant, and the turbulence generates larger vortex structures above the wing’s upper-right region. The presence of oscillating turbulence led to an increase in the airfoil’s peak lift force. The lift-to-drag ratio of the airfoils reached a maximum in the range of 5°–10° angle of attack. Improved deep stall behavior and lift generation at small angles of attack were more pronounced under turbulence with smaller oscillation amplitudes.